Apparatus for atmospheric sounding and celestial observing



Jan. 2, 1962 D A. DEISINGER APPARATUS FOR ATMOSPHERIC SOUNDING Filed Jan. 5, 1959 AND CELESTIAL OBSERVING 2 Sheets-Sheet -1 DELBERT A. DE/SIIVGER.

BYWMW 7 ATTORNEY Jan. 2, 1952 Filed Jan. 5, 1959 A. DEISINGER AND CELESTIAL OBSERVING 2 Sheets-Sheet 2 37X FIG. 4

ANTENNA III] 1 4 GROUND 38x TRANSMITTER I PHOT TUBE I AUTOMAT'C NAVIGATION L D'RECT'ON COUPLER 45 FINDER 43 PULSING 7 l 33 I MEANS GL'DE SPEED AUTOMATIC POWER SENSOR SWITCH SUPPLY VERTICAL GYRO YAW ROLL I? I6 18 SERVO SEW SURE-( CODE CODE CODE RESPONSIVE RESPONSIVE RESPONSIVE RELAY RELAY RELAY SWITCH SWITCH SWITCH 46 POWER l l l SUPPLY I I h FIG. 5

INVENTOR ELAY RAND DELBERT A DE/Sl/VGEH. PRIMER BY f \\\\\U 1/ i A T TOR/V5 X United States Patent APPARATUS FOR ATMOSPHERIC SOUNDING AND CELESTIAL OBSERVING Delbert A. Deisinger, 16 Richard Lane, West Long Branch, NJ.

Filed Jan. 5, 1959, Ser. No. 785,095 5 Claims. (Cl. 2442) (Granted under Title 35, US. Code (1952) sec. 266) The invention described herein may be manufactured and used by or for the Government for governmental purposes without the payment of any royalty thereon.

The invention relates to the provision of a vehicle for carrying radiosonde or other atmospheric sounding devices and means for controlling their return to a launching site or other accessible location.

The invention is directed particularly to the specialized techniques wherein lighter than air lifting devices such as balloons are used to carry instruments or other devices to substantial heights above the earth. An example of such techniques is that wherein balloons of the expandable type are used for obtaining weather data.

In gathering such data it has been the usual procedure to house the instruments in a small container and construct the devices such as the radio transmitter and the sensing means within the container as small and light in weight as is practical. The container and instruments are hung from the balloon and a parachute is provided to control the descent of the instruments. During the flight of the balloon and the descent of the radiosonde, data signals are transmitted to a receiver on the ground.

The balloon is so constructed that it will burst and separate itself from the parachute at a predetermined height. The parachute will then open and carry the instruments back to earth. in such a system no directional control can be exercized over the descent of the radiosonde as a result of which it usually is carried to a point remote from the launching site where it is difficult to find. Many times the instruments are lost.

In the present invention the descent of the instruments is under control and the data gathering equipment or other devices may then be recovered without damage thereto. Moreover the present invention provides a specially devised vehicle for the equipment which is capable of carrying a substantially greater load than hitherto was possible. Consequently more equipment may be carried and since safe recovery of the equipment is quite certain it may be of better quality and more precise in operation because itsrepeated use is assured.

The improvements over present equipment are achieved by providing a remotely controllable vehicle to carry the pay load. The vehicle desirably ,is a heavier than air device of the glider type having electromechanical controls automatically operable to return the vehicle to or near its launching site. This vehicle is operated in conjunction with a ground radio transmitter which is capable of guid-,

ing the glider to a desired location on its return to earth I where it may be safely landed.

Elevation of the glider desirably is accomplished by an expendable balloon which takes the glider up to the desired height at which time it is cut loose from the balloon and starts to glide toward the earth carrying the radiosonde or other equipment. When the glider is vdetached from the balloon a switch is actuated to energize an automatic homing system which glides the vehicle to or near to its launching site. During its ascent the equipment within the glider has transmitted desired data to a received at ground level. The homing system operates in conjunction with an omnidirectional radio transmitter at the launching site or other accessible location. This transmitter desirable functions at relatively high frequency to provide for satisfactory reception of the signals ice by a directional type antenna such as a dish type parabola.

A more detailed description will be set forth hereinafter to more clearly present the invention and to indicate the scope thereof.

A primary object of the invention is to provide a safe recovery of airborne objects carried in an unmanned vehicle.

A further object of the invention is to provide an unmanned vehicle particularly adapted for elevating instruments such as meterological sensing devices and returning the vehicle safely to earth at a predetermined location.

A still further object of the invention is to provide a system as outline wherein a lighter than air device lifts the vehicle and a heavier than air gliding vehicle carries and returns the instruments to its launching site.

Other objects and features of the invention will more fully appear from the following description and will be particularly pointed out in the claims.

To provide a better understanding of the invention a particular embodiment thereof will be described and illustrated in the drawings wherein:

FIG. 1 is a general view of the complete apparatus in flight.

FIG. 2 is detail view of the means for disconnecting the balloon from the glider.

FIG. 3 is a general block diagrammatic illustration of the automatic homing equipment for controlling the gliders descent.

FIG. 4 is a block diagram showing the components of a suitable system for controlling the glider during its return to earth.

FIG. 5 is a general view of a suitable means for activating a parachute for assisting in landing the glider.

The novel combination of the invention basically includes a balloon 10 to which an unmanned glider 1-1 is attached. The glider acts as a vehicle to carry atmospheric measuring equipment or other devices aloft. Ground transmitting equipment both automatic and manual act thru controls in the glider to return it safely to its launching site or other location after it has been detached from the balloon.

The balloon 10 may desirably be of the expendable type with capacity to carry the glider to its predetermined maximum height and may be constructed to burst when the required elevation is reached thereby causing the glider to return to earth. A means for positively releasing the glider from the balloon will be described hereinafter in which case the bursting type balloon need not be used.

The glider may desirably be small compared to a manned type heavier than air vehicle and may be substantially smaller than the so called drone used for military experimentation. For use in the present invention it would have no power plant. The fusilage 12 serves as the container for the data gathering instruments and the automatic guidance equipment. The data gathering and transmitting equipment shown generally at 13 is connected to a suitable antenna 14 so positioned and designed that it will radiate and receive signals of maximum energy. The equipment 13 may be of conventional construction and need not be described. Desirably the data is recorded or transmitted or both during the ascent of the glider.

The glider is provided with Wings 15 having the usual ailerons 16 at their trailing edge. For right and left steering or yaw control a rudder 17 is provided and for pitch control the glider is equipped with suitable elevators 18. Although no plan view of the glider is illustrated it is considered that such illustration is not necessary since least two ailerons is well known.

For landing purposes skids or skis 19 are provided although wheels may also be used in place of skis.

The control elements for the glider are also received within the fusilage and are indicated generally at 20. In addition the means for supporting and disconnecting the glider from the balloon is also received within the insilage. As shown in FIG. 1 such means 21 is rigidly secured to the framework of the glider and normally serves to anchor the end of the supporting cable 22 extending from the glider to the balloon. While any suitable structure may be employed for the device '21 a desirable arrangement is shown in FIG. 2 wherein the cable 22 passes thru the wall of a suitable casing 23 and is secured to a holding' bar 24 pivoted within the casing. The cable is provided with a loop 25 within which the bar 24 is received. The free end of the bar 24 is held against the pull of the cable 'by engagement with a lever 26 pivoted near its mid point to the casing 23. The upper end of the lever 26 is pivotally connected to one end of a bellows type atmospheric pressure responsive means 27, the other end of which is anchored to the casing.

The bar 24 is provided with a downwardly extending arm 28 which engages and normally locks an arm 29 pivotally connected to an electric switch 30. The arm 29 is biased upwardly by a spring 31 and the switch is provided with terminals 32.

In operation as the glider is elevated the atmospheric pressure reduces and at a predetermined elevation the change in pressure causes the bellows 27 to expand sufliciently to release the bar 24 which rotates on its pivot allowing the loop 25 to slide off the end of the bar thus separating the balloon and the glider. At the same time the arm 28 of the lever 24 releases the lever 29 which is actuated by the spring 31 to close the circuit thru the terminals 32 connected in the leads from a power supply 33. This activates an automatic homing system which takes over the lider controls to guide the vehicle to its predetermined landing site.

The means for accomplishing the return of the glider may consist of any suitable arrangement of aerodynamic controls such as rudder, ailerons and elevators on the vehicle acting in conjunction with the automatic homing system actuated from an omnidirectional ground transmitter 34.

One suitable combination of elements for accomplishing the desired result will be briefly described and is shown block diagrammatically in its basic form in FIG. 3 to consist of two essential sections an automatic direction finder 35 and an automatic pilot 36. The automatic direction finder has means for obtaining orientation information relative to its landing site and transmits the information to the automatic pilot 36 wherein it is evaluated in terms of mechanical forces acting respectively upon the ailerons 16, the rudder 17 and the elevators 18 of the glider to pilot the same in a homing direction. It will be understood however that other systems may be used without departing from the invention. 7

FIG. 4 illustrates diagrammatically a somewhat expanded presentation of the system referred to above. When the glider is detached from the balloon the switch 30 connects the automatic direction finder to its power source 33 which immediately activates the complete system. The controls on the glider being preset to a normal gliding position, will cause the vehicle to start its glide to earth. At this time the antenna 37 which is stantly measure the aximuth angles between the antenna axis and the longitudinal axis of the glider.

These angles are interpreted in terms of voltages and are fed to the section of the system termed the automatic pilot. Within this section a navigation coupler 38 receives the angle data and transforms it into electrical quantities based upon the navigational requirements to efiectithe required correctional turn to right or left. These quantities are fed to the yaw or azimuth control unit 39 which acts thru a suitable servo to operate the rudder 17. I

Signals from the navigation coupler are also fed to the roll control unit 40 which acts thru a servo to operate the ailerons 16 to roll the glider into the correct angle which acts in conjunction with the rudder deflection to obtain the required turn toward the transmitter. The correct roll angle is further held under control by a vertical gyro 41 which establishes a constant vertical reference axis. The gyro constantly indicates to the roll control 40 the roll angle of the glider at any given instant. 'This data when correlated to the navigation information maintains the correct roll angle.

The pitch angle is established from data supplied by the automatic direction finder. This data is supplied to the pitch control unit 42 which in turn receives alignment data from the gyro 41. This integrated data acts thru a servo to operate the elevators 18 to establish the correct glide angle. The glide angle also is modified by the glide speed sensor 43 connected to the pitch control unit. The sensor 43 carries a pitot tube 44 acting in the known manner to assist in maintaining a substantially constant glide speed.

It will be noted that in each case the output of the yaw control 39, the roll control 40 and the pitch control 42 acting thru their respective servos results in a physical force which is transmitted to the respective aerodynamic controls 17, 16 and 18 by suitable force transmitting means such as cable systems 56.

The above homing system automatically brings the glider to earth close to the transmitter 34. Thus the equipment and theglider are safely returned and may be used repeatedly.

As the glider nears its landing destination it may also be desirable to provide emergency control means when the vehicle reaches its final landing stages to avoid objects or correct for insuflicient automatic control and thus insure landing with a greater factor of safety. This may be done by a manually controlled pulsing device 45 connected to the transmitter 34. This device may function according to a predetermined code which would in turn permit actuation of the various controls of the glider thru the selective actuation of relays which respond to the aforementioned code. Any suitable manual controls can be employed however to provide the necessary guidance.

Such manual control. is illustrated diagrammatically in FIG. 4 wherein an additional antenna 46 on' the glider is connected to three radio responsive relay actuated Y Switches 47, 48 and 49 which selectively actuate the servos controlling the gliders flight. Thus a desired manual control of the vehicle may be accomplished. Control of the glider would be effected by momentary actuation of the glider controls coupled with direct observation of the glider by the operator. Succeeding coded actuations being made as required to safely land the glider.

A further refinement which may be useful in an emergency is to provide a parachute for landing the glider which would desirably be released when the glider was nearing the ground. A conventional storing and releasing means may be provided for this purpose. As shown the parachute 50 is packed in a metal container 51 received within the fuselage of the glider. The. chute is forcibly ejected from the container in any suitable manner such as by firing a charge of gas 52 in the base of the container. A spring biased door 52 in the wall of the glider aeraaee is thrown open by the exploding charge and the chute is blown into operative position. Its anchoring cord 53, is secured to the glider, and supports the vehicle while it is lowered safely to earth.

Ejection of the parachute is accomplished from the ground by pulsing the radio transmitter 34 according to a prearranged coded response in a suitable relay actuated primer 55 connected to the antenna 45. The relay and primer may act thru a local power supply to fire the gas charge as is commonly done in such devices. Other means for ejecting the parachute may however be used.

What is claimed is:

1. Apparatus for atmospheric sounding and celestial observing comprising a balloon, an unmanned glider to carry data gathering equipment, means to suspend the glider from the balloon, automatic means to detach the balloon from the glider when a predetermined elevation is reached, maneuverable aerodynamic controls on said glider, a ground radio transmitter, an automatic direction finding antenna on said glider receiving energy from said transmitter, automatic pilot means in the glider receiving data from said direction finding antenna and connections from said automatic pilot equipment to said aerodynamic controls whereby the glider when released is returned to earth guided in its direction of flight by said ground transmitter.

2. Apparatus for atmospheric sounding and celestial observing comprising a balloon, an unmanned glider, to carry data gathering equipment, a cable supporting the glider from the ballon, automatic means to detach the balloon from the glider by releasing said cable when a predetermined elevation has been reached, maneuverable aerodynamic controls on said glider, an omnidirectional ground radio transmitter, an automatic direction finding antenna on said glider receiving signals from said transmitter, automatic piloting means in the glider connected to the output of said automatic direction finding antenna and receiving guidance data therefrom, said automatic piloting means acting to create physical forces for actuating said aerodynamic controls, means for transmitting said forces to said controls and means for activating said automatic direction finding antenna and automatic pilot when said balloon is detached from said glider whereby said glider is piloted to said transmitter.

3. Apparatus for atmospheric sounding and celestial observation comprising a balloon, an unmanned glider to carry data gathering equipment, means to suspend the glider from the balloon, automatic means to detach the balloon from the glider when a predetermined elevation is reached, maneuverable aerodynamic controls on said glider consisting of a rudder, ailerons and elevators, an omnidirectional ground radio transmitter, an antenna of the dished parabola type on said glider having a narrow angle beam receiving signals from said transmitter, automatic means for maintaining the beam axis of said antenna aligned toward said transmitter, automatic direction finding means for measuring the angles between the antenna beam axis and the axis of the glider, an automatic pilot in said glider responsive to signals from said direction finding means proportional to the said measured angles, said automatic pilot having means to create physical forces for actuating said aerodynamic controls, means for transmitting said forces to said controls whereby the glider is piloted to said ground transmitter.

4. Apparatus for atmospheric sounding and celestial observing according to claim 1 and code pulsing means connectable to and operable to transmit coded pulses from said ground transmitter, a second receiving antenna on said glider, radio responsive relay switches on said glider connected to said antenna and operable thru an established pulse code to selectively manually actuate said aerodynamic controls to control the ground approach flight of the glider.

5. Apparatus for atmospheric sounding and celestial observing according to claim 1 and code pulsing means connectable to said ground transmitter, a parachute attached to said glider and normally secured in folded condition, a second antenna on said glider, radio actuated ejecting means connected to said second antenna operable to extend said parachute into operating position upon reception of a prearranged code signal from said transmitter.

References Cited in the file of this patent UNITED STATES PATENTS 2,585,030 Nosker Feb. 12, 1952 2,717,309 Campbell Sept. 6, 1955 2,796,604 Snodgrass June 18, 1957 2,808,999 Chenery Oct. 8, 1957 2,876,677 Clark Mar. 10, 1959 

